Numerical Modeling of Internal Flow Aerodynamics. Part 2: Unsteady Flows

摘要

It has been widely reported in the open literature that large segmented and axisymmetric Solid Rocket Motors (SRM) are subject to pressure oscillations caused by vortex shedding at annular restrictors or cavities in the grain, and acoustic feedback resulting from impingement of the vortices on the nozzle or other obstacles. If they are well suited for combustion instabilities studies in tactical rocket motors, acoustic balance methods have proven inefficient in predicting stability of large segmented rocket motors (e.g. Ariane 5 MPS and Titan IV SRMU).